CN1582364A - Gas turbine group - Google Patents
Gas turbine group Download PDFInfo
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- CN1582364A CN1582364A CNA028220862A CN02822086A CN1582364A CN 1582364 A CN1582364 A CN 1582364A CN A028220862 A CNA028220862 A CN A028220862A CN 02822086 A CN02822086 A CN 02822086A CN 1582364 A CN1582364 A CN 1582364A
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- Prior art keywords
- gas turbine
- cooling
- turbine group
- mass flow
- cooling air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
- F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
- F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/601—Fluid transfer using an ejector or a jet pump
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The aim of the invention is to assist the cooling of an air-cooled gas turbine group. To this end, means for increasing the pressure of a flowing cooling air are placed inside cooling air lines of the cooling system. In one embodiment, the cooling system (17) is supplied with high-pressure compressor air from the final stages of the compressor (1) of a gas turbine group (1, 2, 3, 4). This cooling system branches into a first branch (18) via which the combustion chamber (2) and the first stages, particularly the first guide vane of the turbine (3) are cooled. A second branch (19) guides cooling air to the other turbine stages. An ejector (20) is provided for increasing, according to need, the available pressure gradient over the first branch (18) of the cooling system. The impelling nozzle (22) of the ejector is supplied with live steam (9) extracted from a waste heat steam generator (51), whereby the supply of live steam can be regulated by a regulating element (21). The invention is proven to be generally suitable for flexibly forming the cooling air admission pressure and thus the cooling air mass flow.
Description
Technical field
The present invention relates to a kind of gas turbine group according to claim 1 preamble.
Background technique
With mutually side by side, on the one hand to the requirement of the high machine part cooling of heat load and on the other hand the requirement of design of Cooling System is improved thereupon to the requirement of the power of gas turbine group and efficient.Therefore must guarantee that enough coolings are beneficial to the reliability of work.On the other hand, should limit the consumption of cooling air as far as possible.Propose in EP62932: the steam that the parts of a gas turbine are used in the closed circulation loop cools off.This requirement has the relatively costly sealing of conduction cooling steam parts.Carry out the cooling of the pure convection current of parts simultaneously; Here abandoned being used to reducing the effect of the cooling film of heat input.At a plurality of other documents,, propose in 161,385: for the parts that cool off the tunicle cooling have used steam or steam-air mixture as EP 684 369 or EP 995 891 and corresponding US6.But this method has consumed many relatively steam flow, and it must satisfy purity and overheated high request, only is the obstruction of the big film-cooling hole of a few tenths of millimeter usually so that can not cause.Promptly enable the steam flow and the quality of steam that provide required, the cooling of gas turbine group also is different from cooling with compressor branch air, promptly do not have intrinsic reliability with steam.
Used the cooling of compressor branch air (Verdichter-Anzapfluft) to have a series of significant advantages afterwards, wherein in order to help working procedure, the cooling air volume of taking-up should be very little always.Later on cooling air system more and more is tending towards according to border work design, so that-from cooling technology level-on disadvantageous operation point, can guarantee enough coolings, but except that absolute demand, no longer consume cooling air in the case.This means, on the one hand working procedure is departed from the response sensitivity height of the design point of cooling, for example when the skew cooling air volume owing to pressure ratio in the machine changes.On the other hand, on a series of other operation points, produce the supercooling of heat-loaded component, the potentiality of power and efficient are not utilized.
Therefore in different documents, for example in EP 1 028 230, propose in the cooling air path, to be provided with variable throttle point, DE 199 07 907 proposes, by can directly regulating the precompression of cooling air with the adjustable compressor work level of the point of branching direct neighbor ground setting of cooling air.Although the enforcement of these measures is to estimate that success will follow, very high naturally the reaching of their cost at all is not suitable for installing additional of existing gas turbine group.In addition, the moveable element of packing in cooling air system has when the mechanical part fault potential risk of blocking cooling-air duct.
When another major issue appears at cooling air is supplied to assembly in combustion chamber regions or the turbo machine first guiding level zone, front side.When the pressure loss of attempting to reduce working medium, when making the pressure at turbine inlet place remain as far as possible pressure near the compressor end thus, enough cooling air mass flows must be arranged by narrow cooling air channels and cooling hole.This needs the relevant pressure on the cooling air system to fall naturally, and wherein the precompression of cooling air system also can not be higher than the pressure of compressor end.Therefore in this respect-finally but be not be entirely satisfactory ground-meet the requirements be: be a side with the power of gas turbine group and efficient and guaranteeing that enough being cooled between the opposing party compromise.
JP 11 182263 and EP 1 128 039 propose: in the cooling air path of a gas turbine additional compressor is set.To make the total pressure of cooling air that the pressure that provides by compressor is provided like this.Should note this: total and certain danger that is provided with of active and moveable element interrelates in the cooling air main flow path, and promptly the function integral body of cooling system is subjected to very big influence when driving part is malfunctioning, and urgent even cooling also no longer may be kept.
Summary of the invention
Task of the present invention is, avoids shortcoming of the prior art on the gas turbine group of the described type of beginning part.
Here at first be to avoid in the cooling air path, being provided with movable parts.Next is, provides cooling air system in this wise, so that the total pressure on cooling air raises or intrinsicly produces reliably, or can guarantee enough urgent coolings at least when the related device fault.
This task will realize by all features of claim 1.
Core of the present invention is, the device of total pressure is provided for raising in air cooled gas turbine group in the passage of conduction cooling air, and when given cooling air takes out pressure and cooling air back pressure, change the cooling air mass flow thus, wherein these devices do not have the parts of motion.The sparger of some available driven medium work can be set in cooling air channels for this reason.
Therefore, especially when firing chamber and the cooling of first turbine stage, inevitably the pressure loss of cooling air is compensated on the scope of necessity at least.In addition, be as the design on basis of the present invention, in the cooling-air duct of strong throttling ,-wherein film-cooling hole also is throttle point on fundamental significance, improves effectively total precompression of cooling air.Another selection in the invention process structure is, abandons the adjusting of inner throttling and cooling air mass flow, and this normally realizes with the form that is contained in the Rectifier plate in the cooling-air duct; And the substitute is, under lower pressure, from compressor, carry out the extraction of cooling air, and raise by the pressure in the cooling air channels and to adjust required total precompression.The present invention also can be suitable for particularly well in addition: preferably according to suitable procedure parameter, change the cooling air mass flow of duration of work.For example use therein in the form of implementation of sparger as the pressure raising device, it is simple relatively, and its mode is only to need directly driven medium mass flow rather than whole cooling air mass flow in a small amount to be exerted one's influence.
Except needn't regulating whole cooling air mass flow and also not needing the advantage of direct intervention main cooling system, with for example in main cooling system variable throttle point compare, can reequip existing gas turbine group relatively simply on level of the present invention.
As the driven medium of described or some spargers well suited be the propellant mass flow, especially be the driving air mass flow higher here than the pressure of driven cooling air mass flow.It can stem from the compressor that is arranged on the outside, but the ground that meets the requirements especially, the also air mass flow that can branch out for the compressor stage by elevated pressures.Conversion ground, and also confirm it is that what to meet the requirements is that an additional compressor is set, it makes the further compression of part stream of the cooling air that the compressor by gas turbine branches out; Further the part stream of the cooling air of compression will use as the driven medium of sparger.
Quality of steam stream also can be suitable as driven medium well in addition, and wherein quality of steam stream is preferably by corresponding overheated.In any case therefore can avoid the condensation in cooling-air duct.Compare as cooling medium with supplying with steam, or be used for pure steam cooling or steam-air mixing cooling, advantage is: only need relatively in a small amount high quality and highly purified steam.Be used for when combined equipment is worked or be used for the heat recovery steam generator of procurement process steam when gas turbine group is provided with, this form of implementation then is favourable.Use in addition as in DE 100 41 413 in the cooling air cooler or the steam that in EP 516 995, in compressor intercooler, produces be used as driven medium and also meet the requirements.
Cooling system is intrinsic reliable all the time in this external design that meets the requirements, because can guarantee the minimum value of cooling air flow all the time when driven medium supply, especially steam are supplied with complete failure.Generally can determine in this respect, its value of the mass flow of driven medium is usually less than 20% of driven cooling air mass flow, be preferably less than 10% of driven cooling air mass flow, especially be less than 5% of driven cooling air mass flow, so driven medium itself is as not significantly effect of cooling medium.
As has been noted, in a preferred implementing form, in the input pipe of the driven medium stream that is connected to sparger, be provided with the device that is used to regulate driven medium stream.
The present invention is particularly suitable for a gas turbine group combined, this gas turbine group is provided with the cooling system of different pressures level, for example a high pressure cooling system and a low pressure cooling system, wherein the high pressure cooling system by from one of compressor not level begin to supply with, and low pressure cooling system is begun to be supplied to by the compressor stage of a centre.A particularly preferred form of implementation is in the case, is provided with some spargers in low pressure cooling system, the driven medium work that branches out from the high pressure cooling system of these spargers.And be proved advantageously, the pressure in the compressor is set up and is passed, and the situation that this is especially such is promptly when cooling off between compression period, under the situation about for example cooling off in compressor.
That especially be fit to is an embodiment according to gas turbine group of the present invention, and it relates to a gas turbine group that is provided with order (series connection) burning, and wherein first firing chamber and first turbo machine cool off system cools by high pressure; And one second firing chamber and one second turbo machine are by the cooling system cooling of low-pressure level.
Description of drawings
Below will describe the present invention in detail by the example shown in the accompanying drawing.
Fig. 1 to 4 represents possible advantageous forms of implementation of the present invention, and they in no case should be understood that for ultimate as the invention of feature in claims.Be omitted for understanding the unwanted details of the present invention.
These embodiments and accompanying drawing should be understood that it only is suggestive, and are used for anything but in the restriction of claims as the invention of feature.
Embodiment
Example shown in Fig. 1 show according to a form of implementation of the present invention, be combined in a gas turbine group in the combined equipment.Compressor 1 with air compression to certain pressure and be transported in the firing chamber 2.Fuel burns in pressurized air in the firing chamber.Formed hot flue gas flow is crossed a turbo machine 3, and wherein this turbo machine will be exported a power, and this power is used for the air horsepower load of a Driven Compressor and an outside, as a generator 4.The decompression flue gas flow that still is on the high-temperature is crossed a heat recovery steam generator 5, and a feed-water quality of flowing through there by 51 pairs of heating surfaces flows heating and makes its evaporation there, and this is before this decompression flue gas is discharged in the atmosphere by a chimney 6.At water-steam side, a feed water pump 7 will be transported to heat exchanger 51 from the quality stream of a container 8, and water is evaporated and makes the steam superheating of formation in this heat exchanger.
Fig. 2 represents to have the gas turbine group of the modern structure type of sequential combustion.This gas turbine group is open by EP 620 362.Compressor 1 pressurized air and the air of high pressure is transported to the first firing chamber 2a, first fuel quantity therein burns.The flue gas that is stressed is partly reduced pressure among the high pressure turbine 3a at first turbo machine, wherein typically reaches 1.5 to 2 pressure ratio (Druckverh ltnis), and still flows to the second firing chamber 2b with high temperature and high pressure.Oxygen content behind first firing chamber in the flue gas is still high relatively, is typically about 15% to 17%.Therefore directly feeding additional fuel and burning in the second firing chamber 2b.The hot flue gas that the is reheated external pressure that will in turbo machine 3b, reduce pressure approx, and be discharged from exhaust side 6.Here also can directly be provided with a unshowned heat recovery steam generator; Gas turbine group with sequential combustion can be adapted at using in the combined equipment in principle particularly well.When reducing pressure in turbo machine 3a and 3b, flue gas will be exported a power, this power powers compressor 1 and a generator 4.Based on the high-pressure ratio that realizes in this gas turbine group, cooling system is made to the two-part with a high pressure cooling system 23 and a low pressure cooling system 24.The high pressure cooling system branches out air from compressor outlet, and cools off the first firing chamber 2a and high pressure turbine 3a with it.Low pressure cooling system 24 branches out air from an intermediate compressor level, and cools off the second firing chamber 2b and low-pressure turbine 3b with it.Two-part of this cooling system are divided and can be accomplished: the high-pressure section in hot gas path is supplied with the cooling air of high pressure, and can avoid being used for the big throttling of high pressure cooling air loss of hot gas path low pressure section cooling at this.Certainly also can realize having cooling system in principle more than two pressure levels.Compressor 1 is divided into the first compressor section 1a and the second compressor section 1b, is provided with an interstage cooler 1c between them.Work by interstage cooler 1c makes the required power reduction of Driven Compressor, and the efficient of gas turbine group and useful work are increased.This effect also can reach by the suction air supersaturation that ejects water in the compressor or have a moisture, and it makes moisture play the effect of the inner strong cooling of compressor based on vaporization.The cooling of air also has another effect in compressor: confirmable as the consideration that the professional workforce learns by simple graded movement, when in compressor during with middle cooling segment work the foundation of pressure transfer to afterwards in the compressor stage.Relative decompression by turbine stage can remain unchanged approx, and the foundation of pressure is transferred among the second compressor section 1b significantly in the compressor stage.Produce obviously reducing of driving pressure difference on the low pressure cooling system 24 thus, and obtained reducing of low pressure cooling air mass flow thus.If low pressure cooling system 24 is determined size in this wise, the cooling air mass flow was enough used when promptly cooling moved in compressor, then when compressor-free cooling operation, will cause the obvious supercooling of low pressure hot gas path, assembly 2b and 3b, will bring bad consequence power and efficient.Therefore, according to the present invention a sparger 20 is arranged in the low pressure cooling system, its driving nozzle 22 is connected with the high pressure cooling system by a controlling mechanism 21.This controlling mechanism 21 is closed or only opens tinily in first working zone of compressor-free cooling; This low pressure cooling system is for the cooling air mass flow design of enough usefulness just.Have the in service of compressor cooling, this controlling mechanism 21 is opened, and at full speed changes pressure ratio the low pressure cooling system in this wise from the high pressure cooling air that drives the nozzle ejection, promptly guarantees enough cooling air mass flows.This system even work automatically to a certain extent: wherein pressure is set up and is transferred among the second compressor section 1b, and raising falls in the pressure that flows usefulness for the sparger driven medium, automatically supports the driving action in the low pressure cooling system thus with adjusting.When the respective design of system, therefore can consider in principle, replace controlling mechanism 21 with the adjusting flow with fixing throttle point, and abandon foreign intervention driven medium stream.Cooling in the middle of being similar to, the adjusting of also available a plurality of guiding levels (Leitreihen) causes the passing that pressure is set up in the compressor, this also can cause that the device that pressure raises compensates by using in cooling air channels for the cooling air mass flow.
Form of implementation shown in Fig. 2 has intrinsic reliable feature.When working, gas turbine group also can automatically provide driven medium to sparger.In the form of implementation shown in Fig. 1, there is the possibility that when raw water service pump 7 faults, loses driven medium; This also means in practice: the heating surface 51 meeting desiccation of heat recovery steam generator 5, so that entire equipment must quit work in the case.Thus, the increased pressure of cooling air is known as intrinsic reliable here.
Correspondingly, Fig. 3 and 4 expresses two forms of implementation of the present invention, though they do not have the inherent reliability of cooling air increased pressure, can on existing equipment, replenish especially simply and install, can guarantee minimum cooling when reaching the system failure that raises when the cooling air total pressure.According to the form of implementation among Fig. 3, go out the part of cooling air 17 and carry and provide ratio piston compressor 1 available high total pressure by an additional compressor 25 in the upstream branch of sparger 20.The part stream of this recompression is used as the driven medium of the driving nozzle 22 of sparger.Additional compressor 25 is driven by a variable motor 26 of rotating speed, and the rotational speed regulation of this motor can reach the adjusting that pressure to be achieved in the cooling air system raises.Fig. 4 then represents: for example compressible ambient air of additional compressor 25; The driving nozzle 22 of sparger 20 can certainly be connected on any external pressure gas system.Even when so effective external system fault, can not make main cooling air path produce fault together yet.Only be to have lost the raising of cooling air total pressure and the cooling air mass flow is reduced.But still continue to keep the minimum cooling air flow that needs, and gas turbine group can work on the power that may reduce free from all inhibitionsly.
The present invention can accomplish in addition: according to the hot gas temperature in the component area of waiting to be cooled cooling air volume is reduced to on the required minimum value of functional reliability, and correspondingly increases when high gas turbine load.
Certainly, only have a firing chamber and only the gas turbine group of a turbo machine also can equip an above-mentioned cooling system with two or more pressure levels.
The present invention also can be easily and other common measure, combines as the structure of the air-cooling apparatus that the professional workforce was familiar with.
The driving nozzle of sparger-when the precompression of driven medium allows, especially can cross critically to be driven like this, that is, the current drainage that drives nozzle is carried out with ultrasonic velocity.The deceleration of driven medium stream can realize that then this will help effectively work by an impact system under the situation of fluid passage respective profile design.
Also other can be installed in principle, for example pressure wave generator is used as the device that improves cooling air pressure in the mode that is fit to.
According to the foregoing description, the of the present invention multiple possible form of implementation of having showed in claims to be characterized for the professional workforce.
Claims (11)
1. gas turbine group has a cooling air system (17; 23; 24), make at least one cooling air mass flow from a compressor (1 by this cooling air system at work; 1a 1b) flows to the high heat load parts (2,3 of gas turbine group; 2a, 2b, 3a 3b), is characterized in that: being provided with at least one cooling-air duct of cooling air system can be by the sparger (20) of driven medium driving, and the total pressure that is used for a cooling air that flows raises.
2. according to the gas turbine group of claim 1, it is characterized in that: driven medium is the propellant mass flow of its total pressure total pressure of being higher than driven cooling air mass flow in the cooling-air duct.
3. according to the gas turbine group of claim 2, it is characterized in that: described propellant mass flow is an air mass flow that is branched out by compressor on the elevated pressures position (23).
4. according to the gas turbine group of claim 2, it is characterized in that: described driving air mass flow be one by external source compressed and supplied gas mass flow.
5. according to the gas turbine group of claim 2, it is characterized in that: the driving nozzle of sparger is connected with the output terminal of an additional compressor, and wherein the input end of additional compressor is connected with the cooling air system of sparger upstream.
6. according to the gas turbine group of claim 1, it is characterized in that: described driven medium is a quality of steam stream (9).
7. according to one gas turbine group in the above claim, it is characterized in that: its value of the mass flow of described driven medium is less than being driven 20% of mass flow, preferably less than being driven 10% of mass flow, especially less than being driven 5% of mass flow.
8. according to one gas turbine group in the above claim, it is characterized in that: be provided with the device (21) that is used to regulate the driven medium mass flow at the input pipe that is used for driven medium.
9. according to one gas turbine group in the above claim, it is characterized in that: this gas turbine group is equipped with a high pressure cooling system (23) and a low pressure cooling system (24), wherein the high pressure cooling system is reached low pressure cooling system and is supplied with by an intergrade (1a) of compressor by a plurality of not supplies of level (1b) from compressor.
10. according to the gas turbine group of claim 9, it is characterized in that: be provided with a sparger (20) in low pressure cooling system (24), this sparger can partly flow as driven medium work by the cooling air from high pressure cooling system (23).
11. the gas turbine group according to claim 9 or 10 is characterized in that: high pressure cooling system (23) is connected with first firing chamber (2a) and one first turbo machine (3a) of a gas turbine group with sequential combustion; And low pressure cooling system (24) is connected with second firing chamber (2b) and second turbo machine (3b) of gas turbine group.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH20152001 | 2001-11-02 | ||
| CH2015/01 | 2001-11-02 | ||
| CH2015/2001 | 2001-11-02 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1582364A true CN1582364A (en) | 2005-02-16 |
| CN100365249C CN100365249C (en) | 2008-01-30 |
Family
ID=4567140
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB028220862A Expired - Fee Related CN100365249C (en) | 2001-11-02 | 2002-10-30 | Gas turbine group |
Country Status (5)
| Country | Link |
|---|---|
| US (2) | US6644012B2 (en) |
| EP (1) | EP1440223B2 (en) |
| CN (1) | CN100365249C (en) |
| DE (1) | DE50208862D1 (en) |
| WO (1) | WO2003038244A1 (en) |
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| CN102155298A (en) * | 2010-01-04 | 2011-08-17 | 通用电气公司 | Ejector/mixer nozzle for noise reduction |
| CN104981588A (en) * | 2013-02-12 | 2015-10-14 | 西门子公司 | Steam-temperature control device for a gas- and steam turbine plant |
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- 2002-10-30 DE DE50208862T patent/DE50208862D1/en not_active Expired - Lifetime
- 2002-10-30 WO PCT/IB2002/004522 patent/WO2003038244A1/en active IP Right Grant
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| CN101660545A (en) * | 2008-08-14 | 2010-03-03 | 通用电气公司 | Ejectors with separably secured nozzles, adjustable size nozzles, or adjustable size mixing tubes |
| CN101660545B (en) * | 2008-08-14 | 2015-06-03 | 通用电气公司 | Ejectors with separably secured nozzles, adjustable size nozzles, or adjustable size mixing tubes |
| CN102155298A (en) * | 2010-01-04 | 2011-08-17 | 通用电气公司 | Ejector/mixer nozzle for noise reduction |
| CN102155298B (en) * | 2010-01-04 | 2015-11-25 | 通用电气公司 | For the sparger/mixer nozzle of noise decrease |
| CN104981588A (en) * | 2013-02-12 | 2015-10-14 | 西门子公司 | Steam-temperature control device for a gas- and steam turbine plant |
| CN104981588B (en) * | 2013-02-12 | 2016-12-14 | 西门子公司 | Vapor (steam) temperature adjusting means for combustion gas and steam turbine plant |
| US10156355B2 (en) | 2013-02-12 | 2018-12-18 | Siemens Aktiengesellschaft | Steam temperature control device for a gas and steam turbine plant |
Also Published As
| Publication number | Publication date |
|---|---|
| US7143573B2 (en) | 2006-12-05 |
| EP1440223A1 (en) | 2004-07-28 |
| DE50208862D1 (en) | 2007-01-11 |
| US20030084656A1 (en) | 2003-05-08 |
| CN100365249C (en) | 2008-01-30 |
| EP1440223B1 (en) | 2006-11-29 |
| WO2003038244A1 (en) | 2003-05-08 |
| US6644012B2 (en) | 2003-11-11 |
| EP1440223B2 (en) | 2017-11-08 |
| US20040025491A1 (en) | 2004-02-12 |
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